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Vinci
Snecma, Ottobrunn LOx/LH2 rocket engine. Upper Stages. In development. Advanced expander cycle cryogenic propellant rocket engine with the capability of five in-space restarts. First hot-fire tests 2005. First flight 2010.

Status: In development. Thrust: 180.00 kN (40,460 lbf). Specific impulse: 467 s. Height: 4.20 m (13.70 ft). Diameter: 2.15 m (7.05 ft).

On 20 May 2005, the Vinci engine performed its first hot-fire test at Lampoldshausen's P4.1 test stand. Use of Vinci in the ESC-B upper stage in place of the HM-7B engine and the ESC-A (Etage Superieur Cryotechnique A) would increase the GTO payload performance of Ariane 5 to 12 metric tons. The Ottobrunn Space Propulsion Centre was responsible for the development of the Vinci Thrust Chamber under contract to Snecma. Ottobrunn developed Vinci's regeneratively cooled combustion chamber; coaxial propellant mixing injectors; dump cooled nozzle extension; gimbal joints; and the LOX and LH2 propellant shut-off valves. Engine length with the deployable nozzle extension retracted was 2.3 m. However completion of development of the ESC-B upper stage, and the Vinci engine, were put on indefinite hold in late 2005. First flight of the Vinci and ESC-B was postponed until sometime after 2010.

Engine: 280 kg (610 lb). Chamber Pressure: 61.00 bar. Restarts: 5.



Subtopics

SPW-2000 SNECMA, Pratt and Whitney LOx/LH2 rocket engine. Design 2000. New upper-stage cryogenic engine for the upgraded Ariane-5, the Atlas-5, and other new vehicles.

Country: France, Germany. Propellants: Lox/LH2. Stages: Ariane 5-2 ESC B. Agency: Ottobrunn, SNECMA.

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